CN112455662B - Aircraft landing gear warning initiation and elimination circuit and method - Google Patents
Aircraft landing gear warning initiation and elimination circuit and method Download PDFInfo
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- CN112455662B CN112455662B CN202010988925.7A CN202010988925A CN112455662B CN 112455662 B CN112455662 B CN 112455662B CN 202010988925 A CN202010988925 A CN 202010988925A CN 112455662 B CN112455662 B CN 112455662B
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- 230000000977 initiatory effect Effects 0.000 title claims abstract description 34
- 238000000034 method Methods 0.000 title claims abstract description 22
- 230000008030 elimination Effects 0.000 title claims abstract description 15
- 238000003379 elimination reaction Methods 0.000 title claims abstract description 15
- 230000003213 activating effect Effects 0.000 claims description 3
- 230000009977 dual effect Effects 0.000 claims description 2
- 210000004899 c-terminal region Anatomy 0.000 description 11
- 238000010586 diagram Methods 0.000 description 5
- 230000001276 controlling effect Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/26—Control or locking systems therefor
- B64C25/28—Control or locking systems therefor with indicating or warning devices
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- Aviation & Aerospace Engineering (AREA)
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- Emergency Alarm Devices (AREA)
Abstract
The application provides an aircraft landing gear warning initiating and eliminating circuit and method, and relates to the field of civil aviation. An aircraft landing gear warning initiating and eliminating circuit comprises a landing gear down-in-place switch, an alarm, a flap warning logic control relay, a first warning control relay, a second warning control relay, a first accelerator position switch, a second accelerator position switch, a flap in-place switch and a warning eliminating device, wherein the alarm is connected with the flap warning logic control relay and the first warning control relay, and the flap warning logic control relay is connected with the flap in-place switch and the second warning control relay; the first warning control relay is connected with the second warning control relay; the warning eliminating device connects the first warning control relay and the second warning control relay. The warning and elimination logic meeting the requirements of CCAR23 navigable regulations can solve the problem of complex traditional warning circuits, and has the characteristics of simple structure, high reliability, low cost and the like.
Description
Technical Field
The application relates to the field of civil aviation, in particular to an aircraft landing gear warning initiating and eliminating circuit and method.
Background
The national aviation general aviation compliance regulations CCAR23.729 (f) landing gear warning, prescribing that for land-based aircraft, the following acoustic or equivalent landing gear warning devices must be provided:
(1) The device will sound continuously when one or more of the throttle is retracted beyond the normal landing approach position and the landing gear is not fully lowered and locked. The throttle stopper is not used as an acoustic device. If the prescribed warning device is provided with a manual disabling measure, the warning system must be designed to: when one or more of the post-throttle warnings have been suspended, then either throttle is reduced to (or beyond) the normal landing approach position, and the warning device is activated;
(2) In normal landing procedures, the device will sound continuously when the flap is lowered to a flap position that exceeds the maximum approach, but the landing gear is not fully lowered and locked. The device has to be provided with manual stopping measures. The flap position sensor may be mounted in any suitable location. The device system may use any part of the device system defined in the present item (f) (1) (including an audible warning device).
In the prior art, china patent of the invention, an amphibious aircraft landing gear retraction mechanism position warning device (application number: 201410588929.0) discloses an amphibious aircraft landing gear retraction mechanism position warning device, which comprises a flight warning computer, a radio altimeter, a flap control system and a landing gear retraction system, wherein the flight warning computer comprehensively processes collected information according to a warning logic judging flow and drives the warning device to provide warning for a unit. The technology has the following defects: [1] the warning circuit is designed for an amphibious exercise machine, and the warning logic is complex; [2] a special alarm computer is needed, and a hardware system is complex; [3] the versatility is not provided.
Therefore, it is necessary to design a general aircraft landing gear warning initiating and eliminating circuit which is simple in circuit and good in universality on the basis of meeting the national aviation general aviation airworthiness regulation CCAR23.729 (f) landing gear warning conditions.
Disclosure of Invention
Based on the above, the application provides the circuit and the method for initiating and eliminating the warning of the undercarriage, which can meet the warning and eliminating logic required by the airworthiness regulation, solve the problem of complex traditional warning circuits, and have the characteristics of simple structure, high reliability, low cost and the like.
According to one aspect of the present application, there is provided an aircraft landing gear warning initiation and cancellation circuit comprising a landing gear down-in-place switch, an alarm, a flap warning logic control relay, a first warning control relay, a second warning control relay, a first throttle position switch, a second throttle position switch, a flap-in-place switch, and a warning cancellation device, wherein,
the first end of the alarm is connected with a power supply, the second end of the alarm is connected with the flap warning logic control relay and the first warning control relay, the flap warning logic control relay is connected with the first end of the first accelerator position switch, the first end of the second accelerator position switch, the first end of the flap in-place switch and the second warning control relay, the second end of the first accelerator position switch is connected with the first warning control relay, the second end of the second accelerator position switch is connected with the second warning control relay, and the second end of the flap in-place switch is grounded; the first warning control relay is connected with the second warning control relay; the first end of the landing gear down-in-place switch is connected with the flap warning logic control relay, the first end of the first throttle position switch, the first end of the second throttle position switch and the second warning control relay; the second end of the landing gear down-to-position switch is grounded; the warning eliminating means connects the first warning control relay and the second warning control relay.
According to a second aspect of the present application, there is provided an aircraft landing gear warning initiation and elimination method comprising:
when the first accelerator is retracted beyond the normal landing approach position to cause the first accelerator position switch to be closed and at least one of the landing gear down-to-position switches is not closed, the alarm sends an alarm through the first warning control relay, the first accelerator position switch and the landing gear down-to-position switch in the non-closed position to be connected with the ground; and
the alarm eliminating device is started to trigger the change of the internal connection mode of the first alarm control relay, so that the alarm is eliminated without a grounding path.
When the first accelerator is retracted to exceed the normal landing approach position and the second accelerator is retracted to exceed the normal landing approach position, the second accelerator position switch is closed and at least one of the landing gear down-to-position switches is not closed, the alarm is connected with the ground through the second warning control relay, the second accelerator position switch and the landing gear down-to-position switch in the non-closed position to give an alarm;
the alarm cannot be eliminated by activating the alarm elimination device.
According to a third aspect of the present application, there is provided an aircraft landing gear warning initiating method comprising:
detecting whether a condition that a flap in-place switch is closed and at least one switch in a landing gear down-place switch is not closed due to the fact that the flap down-place exceeds a normal landing approach position is met; and
in the event that the condition is met, the alarm sounds an alarm by the flap warning logic controlling the relay and landing gear down-to-position switch in the non-closed position to ground.
The alarm cannot be eliminated by activating the alarm elimination device.
The circuit and the method for initiating and eliminating the warning of the aircraft landing gear have the characteristics of clear control logic, simple circuit structure and high reliability, are universal, and are suitable for initiating and eliminating the warning of the aircraft landing gear of a common model.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the description of the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present application, and that other drawings can be obtained by those skilled in the art from these drawings without departing from the scope of protection of the present application.
FIG. 1 is a schematic structural diagram of an aircraft landing gear warning initiation and cancellation circuit according to one embodiment of the present application.
FIG. 2 is a block diagram of an aircraft landing gear warning initiating and eliminating circuit according to one embodiment of the present application. FIG. 3 is a flow chart of an aircraft landing gear warning initiation and elimination method according to an embodiment of the present application.
Detailed Description
The following description of the embodiments of the present application will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are some, but not all, of the embodiments of the present application. All other embodiments, which can be made by those skilled in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application.
According to one aspect of the present application, an aircraft landing gear warning initiation and elimination circuit is provided. FIG. 1 is a schematic structural diagram of an aircraft landing gear warning initiation and cancellation circuit according to one embodiment of the present application. As shown in fig. 1, the landing gear warning initiating and eliminating circuit of the aircraft comprises an alarm, a flap warning logic control relay, a first warning control relay, a second warning control relay, a first throttle position switch, a second throttle position switch, a flap in place switch, a landing gear down in place switch and a warning eliminating device.
In fig. 1, a first end of an alarm is connected with a power supply, a second end of the alarm is connected with a flap warning logic control relay and a first warning control relay, the flap warning logic control relay is connected with a first end of a first throttle position switch, a first end of a second throttle position switch, a first end of a flap in-place switch and the second warning control relay, a second end of the first throttle position switch is connected with the first warning control relay, a second end of the second throttle position switch is connected with the second warning control relay, and a second end of the flap in-place switch is grounded; the first warning control relay is connected with the second warning control relay; the first end of the landing gear down-in-place switch is connected with the flap warning logic control relay, the first end of the first throttle position switch, the first end of the second throttle position switch and the second warning control relay; the second end of the landing gear down-to-bit switch is grounded; the warning eliminating device connects the first warning control relay and the second warning control relay.
In fig. 1, the number of landing gear down-to-in-place switches may be one, two, three, etc. In one particular embodiment, the number of landing gear down-to-position switches is 3, such as, for example, a nose landing gear down-to-position switch, a left landing gear down-to-position switch, and a right landing gear down-to-position switch. Thus, according to the circuit shown in fig. 1, the first end of the nose landing gear down-in-place switch, the first end of the left landing gear down-in-place switch, and the first end of the right landing gear down-in-place switch are respectively connected to the flap warning logic control relay, the first end of the first throttle position switch, the first end of the second throttle position switch, and the second warning control relay, and the second end of the nose landing gear down-in-place switch, the second end of the left landing gear down-in-place switch, and the second end of the right landing gear down-in-place switch are respectively grounded.
In fig. 1, the first and second throttle position switches may be embodied as a left and right throttle position switch of the aircraft or as a right and left throttle position switch of the aircraft. The alarm includes a buzzer. The flap warning logic control relay includes an electromagnetic relay, such as 1432875-1 from TE. The first warning control relay or the second warning control relay includes a dual coil electromagnetic relay, for example, DS2E-ML2-DC24V in loose. The landing gear down-to-position switch, the first throttle position switch, and the second throttle position switch include travel switches, such as 1SE1 of honeywell.
FIG. 2 is a block diagram of an aircraft landing gear warning initiating and eliminating circuit according to one embodiment of the present application. As shown in fig. 2, the landing gear warning initiating and eliminating circuit of the aircraft comprises a power supply, an alarm, a flap warning logic control relay, a first warning control relay, a second warning control relay, a first throttle position switch, a second throttle position switch, a flap in place switch, a landing gear down in place switch and a warning eliminating device.
In fig. 2, the power supply is embodied as a +28v bus bar. The first end of the alarm is connected with a power supply, and the second end of the alarm is connected with the flap warning logic control relay and the first warning control relay. Specifically, in the embodiment shown in FIG. 2, the alarm second end connects pin 87 of the flap warning logic control relay and pin 11 of the first warning control relay.
In fig. 2, the flap warning logic control relay connects the first end of the first throttle position switch, the first end of the second throttle position switch, the first end of the flap in place switch, and the second warning control relay. Specifically, in the embodiment shown in FIG. 2, pin 30 of the flap warning logic control relay connects the first end (C-terminal) of the first throttle position switch, the first end (C-terminal) of the second throttle position switch, and pin 4 of the second warning control relay; pin 85 of the flap warning logic control relay connects the flap to a first end (C-terminal) of the in-place switch.
In fig. 2, the second end of the first throttle position switch is connected to the first warning control relay, the second end of the second throttle position switch is connected to the second warning control relay, and the second end of the flap in place switch is grounded. Specifically, in the embodiment shown in fig. 2, the NC terminal of the first throttle position switch is connected to the first warning control relay pin 15, while the NO terminal of the first throttle position switch is connected to the first warning control relay pin 13, the NC terminal of the second throttle position switch is connected to the second warning control relay pin 15, and the NO terminal of the second throttle position switch is connected to the second warning control relay pin 13.
In fig. 2, the first warning control relay is connected with the second warning control relay. Specifically, in the embodiment shown in fig. 2, pins 1, 2, 4, and 8 of the first warning control relay are connected to pins 1, 2, 8, and 11 of the second warning control relay, respectively.
The first end of the landing gear down-in-place switch is connected with the flap warning logic control relay, the first end of the first throttle position switch, the first end of the second throttle position switch and the second warning control relay; the second end of the landing gear down-to-position switch is grounded. Specifically, in the embodiment shown in FIG. 2, the first end of the landing gear down-to-position switch (NC end) connects pin 30 of the flap warning logic control relay, the first end of the first throttle position switch (C end), the first end of the second throttle position switch (C end), and pin 4 of the second warning control relay; the landing gear down-to-bit switch has a second end (C-terminal) grounded.
In the embodiment shown in fig. 2, the number of landing gear down-to-position switches is 3: a nose landing gear down-position switch S1, a left landing gear down-position switch S3, and a right landing gear down-position switch S4. It should be noted that, although the number of the nose landing gear down-position switches, the left landing gear down-position switches, and the right landing gear down-position switches in fig. 2 is one, that is, S1, S3, and S4, respectively, the number of the nose landing gear down-position switches, the left landing gear down-position switches, and the right landing gear down-position switches may be two or more, respectively. In practical application, the closed position and the non-closed position of the plurality of front landing gear down-to-position switches are kept consistent, the closed position and the non-closed position of the plurality of left landing gear down-to-position switches are kept consistent, and the closed position and the non-closed position of the plurality of right landing gear down-to-position switches are also kept consistent. According to the circuit shown in fig. 2, the first end (NC end) of the nose landing gear down-in-place switch, the first end (NC end) of the left landing gear down-in-place switch, and the first end (NC end) of the right landing gear down-in-place switch are respectively connected to the pin 30 of the flap warning logic control relay, the first end (C end) of the first throttle position switch, the first end (C end) of the second throttle position switch, and the pin 4 of the second warning control relay, and the second end (C end) of the nose landing gear down-in-place switch, the second end (C end) of the left landing gear down-in-place switch, and the second end (C end) of the right landing gear down-in-place switch are respectively grounded.
In fig. 2, the warning eliminating means connects the first warning control relay and the second warning control relay. Specifically, in the embodiment shown in fig. 2, one end of the alarm eliminating device is connected to the power supply, and the other end is connected to the first alarm control relay pin 1 and the pin 1 of the second alarm control relay.
In the embodiment shown in fig. 2, the NO end and NC end of the first throttle position switch, the second throttle position switch, the flap in place switch, and the landing gear down in place switch represent the closed state and the non-closed state of the corresponding switches, respectively, wherein the closed states of the first throttle position switch, the second throttle position switch, and the flap in place switch represent that the first throttle, the second throttle, and the flap positions exceed the normal landing approach position, respectively, and the closed state of the landing gear down in place switch represents that the landing gear is down in place; the non-closed states of the first throttle position switch, the second throttle position switch and the flap in-place switch respectively indicate that the positions of the first throttle, the second throttle and the flap do not exceed the normal landing approach position, and the non-closed state of the landing gear in-place switch indicates that the landing gear is not in place.
The specific arrangement and connection of the circuit components, in particular the pin arrangement and connection of the flap warning logic control relay, the first warning control relay and the second warning control relay, is shown in the embodiment shown in fig. 2. However, it should be noted that the pin arrangement and connection relationships of the circuit components of fig. 2, particularly the flap warning logic control relay, the first warning control relay, and the second warning control relay, are not unique or fixed, so long as the China civil aviation general aviation applicable regulations CCAR23.729 (f) landing gear warning conditions and warning logic can be satisfied, and those skilled in the art will recognize that other components, other pin arrangements, and other connection relationships, which can be used as the flap warning logic control relay, the first warning control relay, and the second warning control relay, are within the scope covered by the present application.
The operation of the landing gear warning initiating and eliminating circuit is described in detail below in accordance with the block diagram of the landing gear warning initiating and eliminating circuit shown in fig. 1 and 2 described above.
As shown in fig. 2, when the first accelerator is retracted beyond the normal landing approach position to trigger the first accelerator position switch S5 to be in the closed position, if at least one of the nose landing gear down-position switch S1, the left landing gear down-position switch S3 and the right landing gear down-position switch S4 is not closed, that is, there is a connection between the C terminal and the NC terminal, the "-" pole of the alarm is connected to the ground through the 11 pin, 13 pin, the NO terminal and the C terminal of the first accelerator position switch S5, and the NC and the C terminal of a landing gear down-position switch of the first warning control relay, and the alarm emits a continuous warning sound at this time because the "+" pole of the alarm is always connected to the +28v power supply.
When the alarm eliminating device K1 is pressed, the SET coil of the first alarm control relay is powered on, the 13 pin is connected with the 9 pin, the 8 pin is connected with the 4 pin, the alarm is stopped when no path is to the ground, and the alarm is eliminated.
At this time, when the second accelerator is retracted beyond the normal landing approach position to trigger the second accelerator position switch S6 to be in the closed position, the "-" pole of the alarm passes through the 11 feet and 13 feet of the second warning control relay, the NO and C feet of the second accelerator position switch S6, and the NC and C ends of the landing gear down-to-position switch are again turned on with the ground, and the alarm continuously emits a warning sound again.
When the first accelerator and the second accelerator are retracted beyond the normal landing approach position to trigger the first accelerator position switch S5 and the second accelerator position switch S6 to be in the closed position, the warning eliminating device K1 is started, the SET coils of the first warning control relay and the second warning control relay are powered on, the 13 feet and the 9 feet are respectively connected, the 8 feet and the 4 feet are connected, the "-" pole of the alarm passes through the 8 feet, the 4 feet and the 8 feet and the 4 feet of the first warning control relay, and the NC and the C end of a landing gear down-position switch are connected with the ground, so that the warning sound of the alarm cannot be eliminated.
The working process of the landing gear warning initiating and eliminating circuit of the airplane under the condition of firstly collecting the first accelerator and then collecting the second accelerator is described above, and the description is not repeated.
When the flap is put down beyond the normal landing approach position, namely the flap in-place switch S7 is closed, the flap warning logic controls the relay to be attracted, if at least one landing gear put-down in-place switch is not closed in the nose landing gear put-down in-place switch S1, the left landing gear put-down switch S3 and the right landing gear put-down switch S4 at the moment, namely the C end is connected with the NC end, the 'pole' of the warning buzzer is connected with the ground through the 87, 30 pins of the flap warning logic control relay, the NC and the C pin of a certain landing gear put-down in-place switch are connected with the ground, and the alarm sends continuous warning sounds which cannot make the stop sound through the warning elimination device.
As can be seen from the above description, when at least one of the landing gear down-to-position switches is not closed, when one of the first throttle and the second throttle exceeds the normal landing approach position, a warning sound is emitted, and the warning can be eliminated; when the positions of the first throttle and the second throttle exceed the normal landing approach position, warning sounds are sent out, and the warning cannot be eliminated; when the flap position exceeds the normal landing approach position, a warning sound is emitted regardless of the positions of the first throttle and the second throttle, and the warning cannot be eliminated. As can be seen, the aircraft landing gear warning initiation and elimination circuitry meets the warning and elimination logic of the airworthiness regulatory requirements.
In accordance with another aspect of the present application, an aircraft landing gear warning initiation and elimination method is provided. FIG. 3 is a flow chart of an aircraft landing gear warning initiation and elimination method according to an embodiment of the present application. As shown in fig. 3, the method includes the following steps.
In step S301, when the first accelerator is retracted beyond the normal landing approach position, causing the first accelerator position switch to be closed and at least one of the landing gear down-in-place switches to be non-closed, the alarm is turned on with the ground through the first warning control relay, the first accelerator position switch, and the landing gear down-in-place switch in the non-closed position.
According to the embodiment shown in fig. 2, when the first throttle is retracted beyond the normal landing approach position to trigger the first throttle position switch S5 to be in the closed position, if at least one of the nose landing gear down-position switch S1, the left landing gear down-position switch S3 and the right landing gear down-position switch S4 is not closed, i.e., there is a C-terminal to be connected to NC, the "-" pole of the alarm is turned on with ground through the 11-leg, 13-leg, NO-and C-terminals of the first throttle position switch S5, and NC and C-terminal of a landing gear down-position switch of the first warning control relay, and since the "+" pole of the alarm is always on with +28v power, the alarm emits a continuous warning sound at this time.
In step S302, the alarm eliminating device is started to trigger the change of the internal connection mode of the first alarm control relay, so that the alarm has no grounding path and eliminates the alarm.
According to the embodiment shown in fig. 2, the alarm canceling device K1 is pressed, at this time the SET coil of the first alarm control relay is powered on, the 13-pin is turned on with the 9-pin, the 8-pin is turned on with the 4-pin, the "-" pole of the alarm has no path to ground, the buzzer is deactivated, and the alarm is canceled.
In step S303, when the second accelerator is retracted beyond the normal landing approach position, causing the second accelerator position switch to be closed and at least one of the landing gear down-in-place switches to be non-closed, the alarm is turned on with the ground through the second warning control relay, the second accelerator position switch, and the landing gear down-in-place switch in the non-closed position.
According to the embodiment shown in fig. 2, when the second throttle retraction exceeds the normal landing approach position triggering the second throttle position switch S6 to be in the closed position, the alarm again continuously sounds a warning by the "-" pole of the alarm through the 11, 13 legs of the second warning control relay, the NO, C legs of the second throttle position switch S6, and the NC and C ends of the landing gear down-to-position switch again being on with ground.
And step S304, starting the warning eliminating device to trigger the change of the internal connection modes of the first warning control relay and the second warning control relay, so that the alarm is connected with the ground through the first warning control relay, the second warning control relay and the landing gear in the non-closed position, and the alarm continuously gives an alarm.
According to the embodiment shown in fig. 2, in the case where the first throttle and the second throttle are both retracted beyond the normal landing approach position to trigger the first throttle position switch S5 and the second throttle position switch S6 to be in the closed position, the SET coils of the first warning control relay and the second warning control relay are energized, the respective 13-foot and 9-foot are turned on, the 8-foot and 4-foot are turned on, the "-" pole of the alarm passes through the 8-foot, 4-foot, 8-foot, 4-foot of the first warning control relay, and the NC and C terminal of a landing gear down-to-position switch are turned on with the ground, and the warning sound of the alarm cannot be canceled.
In step S305, when the flap is put down beyond the normal landing approach position so that the flap in-place switch is closed and at least one of the landing gear put down in-place switches is not closed, the alarm is turned on with the ground by the flap warning logic control relay and the landing gear put down in-place switch in the non-closed position.
When the flap position exceeds the normal landing approach position, a warning sound is emitted regardless of the positions of the first throttle and the second throttle, and the warning cannot be eliminated. Thus, the present application also provides an aircraft landing gear warning initiating method:
detecting whether a condition that a flap in-place switch is closed and at least one switch in a landing gear down-place switch is not closed due to the fact that the flap down-place exceeds a normal landing approach position is met; and
in the event that the condition is met, the alarm sounds an alarm by the flap warning logic controlling the relay and landing gear down-to-position switch in the non-closed position to ground.
According to the embodiment shown in fig. 2, when the flap is put down beyond the normal landing approach position, namely the flap in-place switch S7 is closed, the flap warning logic controls the relay to be engaged, if at least one of the nose landing gear put down in-place switch S1, the left landing gear in-place switch S3 and the right landing gear in-place switch S4 is not closed, namely the C end is connected with the NC end, the "-" pole of the warning buzzer is connected with the ground through the 87, 30 pins of the flap warning logic control relay, and the NC and the C pin of a certain landing gear put down in-place switch are connected with the ground, and the alarm emits a continuous warning sound, so that the stopping sound cannot be generated through the warning eliminating device.
The circuit and the method for initiating and eliminating the warning of the aircraft landing gear have the characteristics of clear control logic, simple circuit structure and high reliability, are universal, and are suitable for initiating and eliminating the warning of the aircraft landing gear of a common model.
The foregoing has outlined rather broadly the more detailed description of embodiments of the present application, wherein specific examples have been provided herein to illustrate the principles and embodiments of the present application, and wherein the above examples are provided to assist in the understanding of the methods and concepts of the present application. Meanwhile, based on the ideas of the present application, those skilled in the art can make changes or modifications on the specific embodiments and application scope of the present application, which belong to the scope of the protection of the present application. In view of the foregoing, this description should not be construed as limiting the application.
Claims (10)
1. An aircraft landing gear warning initiating and eliminating circuit comprises a landing gear down-in-place switch, an alarm, a flap warning logic control relay, a first warning control relay, a second warning control relay, a first throttle position switch, a second throttle position switch, a flap in-place switch and a warning eliminating device,
the first end of the alarm is connected with a power supply, the second end of the alarm is connected with the flap warning logic control relay and the first warning control relay, the flap warning logic control relay is connected with the first end of the first accelerator position switch, the first end of the second accelerator position switch, the first end of the flap in-place switch and the second warning control relay, the second end of the first accelerator position switch is connected with the first warning control relay, the second end of the second accelerator position switch is connected with the second warning control relay, and the second end of the flap in-place switch is grounded; the first warning control relay is connected with the second warning control relay; the first end of the landing gear down-in-place switch is connected with the flap warning logic control relay, the first end of the first throttle position switch, the first end of the second throttle position switch and the second warning control relay; the second end of the landing gear down-to-position switch is grounded; the warning eliminating means connects the first warning control relay and the second warning control relay.
2. The circuit of claim 1, wherein the landing gear down-to-position switch comprises a nose landing gear down-to-position switch, a left landing gear down-to-position switch, and a right landing gear down-to-position switch, a first end of the nose landing gear down-to-position switch, a first end of the left landing gear down-to-position switch, and a first end of the right landing gear down-to-position switch are respectively connected to the flap warning logic control relay, the first end of the first throttle position switch, the first end of the second throttle position switch, and the second warning control relay, and a second end of the nose landing gear down-to-position switch, a second end of the left landing gear down-to-position switch, and a second end of the right landing gear down-to-position switch are respectively grounded.
3. The circuit of claim 1, wherein the alarm comprises a buzzer.
4. The circuit of claim 1, wherein the flap warning logic control relay comprises an electromagnetic relay.
5. The circuit of claim 1, wherein the first warning control relay or the second warning control relay comprises a dual coil electromagnetic relay.
6. The circuit of claim 1, wherein the landing gear down-to-position switch, the first throttle position switch, and the second throttle position switch comprise travel switches.
7. An aircraft landing gear warning initiating method based on the aircraft landing gear warning initiating and eliminating circuit of any one of claims 1 to 6, comprising:
when the first accelerator is retracted beyond the normal landing approach position to cause the first accelerator position switch to be closed and at least one of the landing gear down-to-position switches is not closed, the alarm sends an alarm through the first alarm control relay, the first accelerator position switch and the landing gear down-to-position switch in the non-closed position being connected with the ground; and
activating the alarm elimination device triggers a change in the internal connection of the first alarm control relay such that the alarm eliminates an alarm without a ground path.
8. The method of claim 7, further comprising:
after the first accelerator is retracted beyond the normal landing approach position, when the second accelerator is retracted beyond the normal landing approach position to cause the second accelerator position switch to be closed and at least one of the landing gear down-to-position switches is not closed, the alarm sends an alarm through the second warning control relay, the second accelerator position switch and the landing gear down-to-position switch in the non-closed position being connected with the ground; and
and starting the warning elimination device to trigger the change of the internal connection modes of the first warning control relay and the second warning control relay, so that the alarm is connected with the ground through the first warning control relay, the second warning control relay and the landing gear in the non-closed position, and the alarm continuously gives out an alarm.
9. The method of claim 7 or 8, further comprising:
when the flap is put down beyond the normal landing approach position to cause the flap in-place switch to be closed and at least one of the landing gear put-down in-place switches is not closed, the alarm sends an alarm through the flap warning logic control relay and the landing gear put-down in-place switch in the non-closed position being connected with the ground.
10. An aircraft landing gear warning initiating method based on the aircraft landing gear warning initiating and eliminating circuit of any one of claims 1 to 6, comprising:
detecting whether a condition is met that a flap put-down exceeds a normal landing approach position, so that the flap in-place switch is closed and at least one switch in the landing gear put-down in-place switch is not closed; and
in the event that the condition is met, the alarm sounds an alarm by the flap warning logic controlling a relay and landing gear down-to-position switch in an unclosed position to ground.
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